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Energies
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Clean Combustion and Heat Transfer of Gas Turbine
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Clean Combustion and Heat Transfer of Gas Turbine

A special issue of Energies (ISSN 1996-1073). This special issue belongs to the section "J1: Heat and Mass Transfer".

Deadline for manuscript submissions: closed (21 September 2023) | Viewed by 2950

Special Issue Editors

Dr. Ningbo Zhao

E-Mail Website
Guest Editor
College of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, China
Interests: gas turbine; combustion; heat transfer
Dr. Hao Zhao

E-Mail Website
Guest Editor
College of Engineering, Peking University, Beijing 100871, China
Interests: chemistry kinetics; extreme combustion; plasma-assisted synthesis; lithium battery
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

As a kind of rotating machinery, the modern gas turbine has been widely used in the fields of propulsion and the power industry. In recent years, a major focus of research has been the increasing demands for the reduction in CO2 emissions and fuel usage, higher thermal efficiency, and lower combustion emission of gas turbine. Therefore, the developments of clean combustion technologies (such as staged combustion, alternative fuels et al.) and enhanced heat transfer of hot components (such as micro cooling, combined cooling et al.) are considered key. This Special Issue aims to encourage researchers to focus on the clean combustion and heat transfer technologies of gas turbines. The topics of interest in this Special Issue include, but are not limited to, the following areas:

  • Advances in combustion or cooling (review paper);
  • Low emission combustion;
  • Alternative fuels;
  • Hydrogen combustion;
  • Ammonium combustion;
  • Combustion instabilities and diagnostics;
  • Pressure gain combustion;
  • Heat transfer in combustor or turbine blades;
  • Secondary air systems;
  • Innovative cooling;
  • Heat exchanger;
  • Advanced measurement technology.

Dr. Ningbo Zhao
Dr. Hao Zhao
Guest Editors

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Energies is an international peer-reviewed open access semimonthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2600 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

 

Keywords

  • gas turbine
  • low emissions
  • alternative fuels
  • hydrogen or ammonium combustion
  • combustion diagnostics
  • combustion instabilities
  • advanced combustion
  • heat transfer and cooling
  • secondary air systems
  • heat exchanger
  • experimental measurement

Published Papers (3 papers)

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Research

21 pages, 5453 KiB  
Article
Fully Coupled Whole-Annulus Investigation of Combustor–Turbine Interaction with Reacting Flow
by Heyu Wang and Kai Hong Luo
Energies 2024, 17(4), 873; https://doi.org/10.3390/en17040873 - 13 Feb 2024
Viewed by 435
Abstract
Micro-gas turbines are used for power generation and propulsion in unmanned aerial vehicles. Technological advancements to enhance their efficiency and fuel adaptability are continuously sought out. As part of a comprehensive study focused on understanding the fundamental performance and emission characteristics of a [...] Read more.
Micro-gas turbines are used for power generation and propulsion in unmanned aerial vehicles. Technological advancements to enhance their efficiency and fuel adaptability are continuously sought out. As part of a comprehensive study focused on understanding the fundamental performance and emission characteristics of a micro gas turbine model, with the aim of finding ways to enhance the operation of micro gas turbines, the current study uses a fully coupled whole-annulus simulation approach to systematically explore the combustor–turbine interaction without compromising the accuracy due to domain truncation. The numerical model is highly complex, spanning aerothermodynamics, fuel vaporization, combustion, and multi-species flow transport. Coupled with the realistic geometries of a representative micro-gas turbine, the proposed numerical model is highly accurate with the capability to capture the complex interaction between the flowfield and the aerothermodynamics and emission performances. The results show that unburnt gaseous Jet-A fuel is carried into the turbine domain through vortical flow structures originating from the combustion chamber. Notably, combustion processes persist within the turbine, leading to rapid Jet-A fuel concentration decay and linearly increasing soot concentration across the turbine domain. The relative circumferential positioning of the combustion chamber and turbine vane (i.e., clocking effects) profoundly influences micro-gas turbine aerothermodynamics and pollutant emissions. Leading-edge impingement hot-streak configurations enhance aerodynamic efficiency, while mid-passage hot-streak configurations mitigate aerothermal heat load and soot emissions. Clocking effects impact all parameters, indicating a complex interplay between the flowfield, aerothermal performance, and pollutant emissions. However, turbine vane heat load exhibits the most significant variations. Full article
(This article belongs to the Special Issue Clean Combustion and Heat Transfer of Gas Turbine)
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25 pages, 12534 KiB  
Article
Numerical Investigation of the Effects of the Hole Inclination Angle and Blowing Ratio on the Characteristics of Cooling and Stress in an Impingement/Effusion Cooling System
by Haiwang Li, Dawei Zhang, Ruquan You, Yifan Zou and Song Liu
Energies 2023, 16(2), 937; https://doi.org/10.3390/en16020937 - 13 Jan 2023
Cited by 2 | Viewed by 1012
Abstract
Due to the uneven temperature field and temperature gradient introduced by an efficient cooling structure, the analysis of the stress field is necessary. In this study, the cooling characteristics and stress characteristics such as the thermal stress and thermomechanical stress of an impingement/effusion [...] Read more.
Due to the uneven temperature field and temperature gradient introduced by an efficient cooling structure, the analysis of the stress field is necessary. In this study, the cooling characteristics and stress characteristics such as the thermal stress and thermomechanical stress of an impingement/effusion cooling system were investigated by employing a fluid–thermal-structure coupling simulation method. The effects of film hole injection angle (30°–90°) and blowing ratio (0.5–2.0) were studied. The results showed that the film hole shape and the non-uniform temperature field introduced by the cooling structure had a great influence on the stress field distribution. With the increase in the blowing ratio, not only the overall cooling effectiveness of the cooling system increased, but the maximum thermal stress and thermomechanical stress near film holes also increased. The cases with a smaller inclination angle could provide a better cooling performance, but caused a more serious stress concentration of the film hole. However, the thermal stress difference at the leading and trailing edges of the film hole increased with a decreasing inclination angle. The cases with a = 30° and 45° showed serious thermal stress concentration near the hole’s acute region. Full article
(This article belongs to the Special Issue Clean Combustion and Heat Transfer of Gas Turbine)
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14 pages, 6120 KiB  
Article
Theoretical and Numerical Study on Thermal Insulation Performance of Thermal Barrier Coatings
by Chao Gao, Yang Liu, Ruquan You and Haiwang Li
Energies 2022, 15(19), 6880; https://doi.org/10.3390/en15196880 - 20 Sep 2022
Cited by 2 | Viewed by 1117
Abstract
In this article, a theoretical 1-D heat transfer model and conjugate heat transfer numerical simulation was carried out to evaluate the thermal insulation of TBCs under different factors. The relationship of temperature-drop between the inner or outer surface of thermal barrier coating (TBC) [...] Read more.
In this article, a theoretical 1-D heat transfer model and conjugate heat transfer numerical simulation was carried out to evaluate the thermal insulation of TBCs under different factors. The relationship of temperature-drop between the inner or outer surface of thermal barrier coating (TBC) was investigated by conjugate heat transfer numerical simulation. The effect of TBC and the coupling between the internal and external heat transfer are obtained, which indicates that TBC and film cooling can both contribute to an overall cooling performance. In addition, the combination of the two results are better results than the two alone. However, the two weaken each other’s contribution to the overall cooling performance. Meanwhile, unlike the effect of film cooling, the change in the internal heat transfer coefficient basically does not affect the thermal insulation effect of coatings. Furthermore, sensitive analysis on the different levels of film cooling and coating’s thermal insulation was conducted to the overall cooling effectiveness, with the blowing ratio ranging from 0.25 to 0.5, thermal resistance ratio ranging from 3 to 9, and the internal heat transfer coefficient ranging from 5000 W/(m2∙K) to 15,000 W/(m2∙K). The results reveal that near the exit of the film hole, film cooling plays a major role in the overall cooling effectiveness. However, with the increase in dimensionless distance, the contribution of coatings and the internal heat transfer coefficient to overall cooling effectiveness gradually increases, especially the contribution of coatings. Full article
(This article belongs to the Special Issue Clean Combustion and Heat Transfer of Gas Turbine)
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